公开(公告)号：US10100647B2

公开(公告)日：2018-10-16

申请号：US14406018

申请日：2013-06-17

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Stephen Mark Molter ,  Mark Edward Stegemiller ,  Shawn Michael Pearson ,  Steven Robert Brassfield

IPC: F01D5/18 ,  B23P15/02 ,  F01D5/20 ,  F01D5/22 ,  F01D9/04

Abstract: A turbine airfoil apparatus includes: an airfoil including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge; an endwall projecting laterally outwardly from the airfoil at one spanwise end thereof, the endwall having an outer surface facing the airfoil and an opposing inner surface; a plenum defined within the endwall between the inner and outer surfaces wherein the plenum is forked in plan view, with at least two branches, each branch having a throat disposed at its upstream end; and at least one film cooling hole passing through the outer surface and communicating with the plenum.

公开(公告)号：US09995148B2

公开(公告)日：2018-06-12

申请号：US13800426

申请日：2013-03-13

Applicant: General Electric Company

Inventor： Stephen Mark Molter ,  Steven Robert Brassfield ,  Shawn Michael Pearson ,  Mark Edward Stegemiller

IPC: F01D5/18 ,  F01D5/14

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D5/18 ,  F01D5/186 ,  F01D5/188 ,  F05D2250/185 ,  F05D2260/20 ,  F05D2260/202 ,  F05D2260/203 ,  F05D2260/2212 ,  Y02T50/67 ,  Y02T50/676

Abstract: Apparatuses and methods are taught for cooling a turbine blade wherein at least one circuit is isolated along a cool suction side of the blade and the circuit turns aft toward a trailing edge.

公开(公告)号：US20150159871A1

公开(公告)日：2015-06-11

申请号：US14407076

申请日：2013-06-13

Applicant: General Electric Company

Inventor： Shawn Michael Pearson ,  Robert Frederick Bergholz ,  Douglas Ray Smith ,  Frederick Alan Buck ,  Stephen Mark Molter ,  Kevin Robert Feldmann

IPC: F23R3/04 ,  F23R3/00

CPC classification number: F23R3/04 ,  F01D5/186 ,  F01D9/023 ,  F01D9/065 ,  F02K1/822 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03042 ,  Y02T50/676

Abstract: A gas turbine engine wall is provided. The wall includes an inner surface and an opposing outer surface having at least one film cooling hole defined therein. The at least one film cooling hole includes an inclined inlet bore that extends from the inner surface and a pair of channels that diverge laterally from an outlet end of the inclined inlet bore. The pair of channels have a substantially constant width and are separated by a ridge to form a boomerang cross-sectional shape.

Abstract translation: 提供燃气涡轮发动机壁。 壁包括内表面和相对的外表面，其中限定有至少一个膜冷却孔。 所述至少一个膜冷却孔包括从内表面延伸的倾斜入口孔和从倾斜入口孔的出口端横向分开的一对通道。 一对通道具有基本上恒定的宽度并且由脊分开以形成回旋形横截面形状。